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HMX添加コンポジット推進薬に関する基礎的研究とその実用化
https://jaxa.repo.nii.ac.jp/records/45133
https://jaxa.repo.nii.ac.jp/records/45133d0db215f-05e2-4031-a9ac-82a73b3421b4
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00875.pdf (4.5 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | HMX添加コンポジット推進薬に関する基礎的研究とその実用化 | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | The Fundamental Study of HMX Composite Propellant and its Practical Application. | |||||||||
| 著者 |
HMX推進薬研究会
× HMX推進薬研究会
× HMX Propellant Research Group
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| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | National Aerospace Laboratory(NAL) | |||||||||
| 書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-875 巻 875, p. 54, 発行日 1985-09 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Synthetic research on HMX composite propellant is described, from the fundamental investigation of propellant burning mechanisms to the demonstration firing test of a full-scale apogee motor. First, the safety and physical properties were examined. By using a new bonding-agent between HMX and HTPB binder for HMX composite propellants, detonability was held in the same manner as the standard propellant without HMX, and some mechanical properties were improved. Second, burning experiments of various HMX/binder strands were made and from these results the mechanism of lowering the burning rate of HMX composite propellants was discussed. Third, firing tests of small-scale rocket motors were conducted under the atmospheric condition for obtaining fundamental combustion characteristics. An example of these characteristics is the absence of combustion instability. Finally, a full-scale (760mm dia.) spherical motor was tested by means of the high altitude test facility. The specific impulse under the vacuum condition was 2.90 KN・s/kg (296kgf・s/kg) at a nozzle expansion ratio of 70. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0875000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-875 | |||||||||
